The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
대리인 / 주소
Edwards, Robin W.
인용정보
피인용 횟수 :
4인용 특허 :
1
초록▼
An active pylon noise control system for an aircraft includes a pylon structure connecting an engine system with an airframe surface of the aircraft and having at least one aperture to supply a gas or fluid therethrough, an intake portion attached to the pylon structure to intake a gas or fluid, a r
An active pylon noise control system for an aircraft includes a pylon structure connecting an engine system with an airframe surface of the aircraft and having at least one aperture to supply a gas or fluid therethrough, an intake portion attached to the pylon structure to intake a gas or fluid, a regulator connected with the intake portion via a plurality of pipes, to regulate a pressure of the gas or fluid, a plenum chamber formed within the pylon structure and connected with the regulator, and configured to receive the gas or fluid as regulated by the regulator, and a plurality of injectors in communication with the plenum chamber to actively inject the gas or fluid through the plurality of apertures of the pylon structure.
대표청구항▼
1. An active pylon noise control system for an aircraft, comprising: a pylon structure connecting an engine system with an airframe surface of the aircraft and comprising at least one aperture to supply a gas or fluid therethrough;an intake portion attached to the pylon structure and configured to i
1. An active pylon noise control system for an aircraft, comprising: a pylon structure connecting an engine system with an airframe surface of the aircraft and comprising at least one aperture to supply a gas or fluid therethrough;an intake portion attached to the pylon structure and configured to intake a gas or fluid;a regulator connected with the intake portion via a plurality of pipes, and configured to regulate a pressure of the gas or fluid;a plenum chamber formed within the pylon structure and connected with the regulator, and configured to receive the gas or fluid as regulated by the regulator;a plurality of injectors in communication with the plenum chamber and configured to actively inject the gas or fluid through the plurality of apertures of the pylon structure. 2. The active pylon noise control system of claim 1, further comprising: a switch attached to the plurality of injectors to selectively direct the gas or fluid to at least one injector of the plurality of injectors. 3. The active pylon noise control system of claim 1, wherein the at least one aperture is formed within a shelf surface or a trailing edge surface of the pylon structure such that the gas or fluid is injected through the shelf surface or the trailing edge surface. 4. The active pylon noise control system of claim 3, wherein an injection angle of the gas or fluid injected from the plurality of injectors is at an angle perpendicular to an exhaust flow direction or in a downstream direction or at an angle therebetween if injected from the shelf surface or a heat shield of the pylon structure, or in a downstream direction if injected from the trailing edge surface of the pylon structure. 5. The active noise control system of claim 4, wherein the intake portion is formed on at least one junction between a nacelle housing the engine system and the pylon structure, on a side surface, upper surface or leading edge surface of the pylon structure, on a side surface or leading edge surface of the pylon structure which is interior to the nacelle or on an inner surface of the nacelle. 6. The active noise control system of claim 5, wherein the pylon further comprises a heat shield, wherein an inner surface of the heat shield facing the core nozzle comprises the at least one aperture. 7. An aircraft system comprising: a fuselage;a wing carried by the fuselage;an engine system comprising:an engine formed above or beneath the wing,a nacelle housing the engine therein, andan engine exhaust nozzle system formed around the engine, and comprising: a fan nozzle configured to receive a fan flow from a fan disposed adjacent to an engine disposed above an airframe surface of the aircraft;a core nozzle disposed within the fan nozzle and configured to receive an Engine core flow;a pylon structure connected to the fan nozzle and structurally attached with an airframe surface to secure the engine system to the aircraft; andan active pylon noise control system comprising: at least one aperture formed on the pylon structure to supply a gas or fluid therethrough;an intake portion attached to the pylon structure and configured to intake the gas or fluid;a regulator connected with the intake portion via a plurality of pipes and configured to regulate a pressure of the gas or fluid;a plenum chamber formed within the pylon structure and connected with the regulator and configured to receive the gas or fluid as regulated by the regulator;a plurality of injectors in communication with the plenum chamber, and configured to actively inject the gas or fluid through the at least one aperture of the pylon structure. 8. The aircraft system of claim 7, wherein the active pylon noise control system further comprises: a switch attached to the plurality of injectors to selectively direct the gas or fluid to at least one injector of the plurality of injectors. 9. The aircraft system of claim 7, wherein the at least one aperture is formed within a shelf surface or a trailing edge surface of the pylon structure such that the gas or fluid is injected through the shelf surface or the trailing edge surface. 10. The aircraft system of claim 9, wherein an injection angle of the gas or fluid injected from the plurality of injectors is at an angle perpendicular to an exhaust flow direction or in a downstream direction or at an angle therebetween if injected from the shelf surface or a heat shield of the pylon structure, or in a downstream direction if injected from the trailing edge surface of the pylon structure. 11. The aircraft system of claim 7, wherein the intake portion is formed on at least one junction between the nacelle and the pylon structure, on a side surface, upper surface or leading edge surface of the pylon structure, on a side surface or leading edge surface of the pylon structure which is interior to the nacelle, or on an inner surface of the nacelle. 12. The aircraft system of claim 7, wherein the pylon further comprises a heat shield, wherein an inner surface of the heat shield facing the core nozzle comprises the at least one aperture.
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